Purpose

This paper aims to investigate the anti-icing performance of the nanosecond dielectric barrier discharge (NSDBD) plasma actuator.

Design/methodology/approach

With the Lagrangian approach and the Messinger model, two different ice shapes known as rime and glaze icing are predicted. The air heating in the boundary layer over a flat plate has been simulated using a phenomenological model of the NSDBD plasma. The NSDBD plasma actuators are planted in the leading edge anti-icing area of NACA0012 airfoil. Combining the unsteady Reynolds-averaged Navier–Stokes equations and the phenomenological model, the flow field around the airfoil is simulated and the effects of the peak voltage, the pulse repetition frequency and the direction arrangement of the NSDBD on anti-icing performance are numerically investigated, respectively.

Findings

The agreement between the numerical results and the experimental data indicates that the present method is accurate. The results show that there is hot air covering the anti-icing area. The increase of the peak voltage and pulse frequency improves the anti-icing performance, and the direction arrangement of NSDBD also influences the anti-icing performance.

Originality/value

A numerical strategy is developed combining the icing algorithm with the phenomenological model. The effects of three parameters of NSDBD on anti-icing performance are discussed. The predicted results show that the anti-icing method is effective and may be helpful for the design of the anti-icing system of the unmanned aerial vehicle.

中文翻译：

---

基于NSDBD等离子驱动器的机翼防冰方法数值研究

目的

本文旨在研究纳秒介质阻挡放电 (NSDBD) 等离子体致动器的抗结冰性能。

设计/方法/方法

使用拉格朗日方法和梅辛格模型，预测了两种不同的冰形状，即雾状和釉面结冰。已经使用 NSDBD 等离子体的现象学模型模拟了平板上边界层中的空气加热。NSDBD 等离子执行器安装在 NACA0012 翼型的前缘防冰区。结合非定常雷诺平均 Navier-Stokes 方程和唯象模型，对翼型周围的流场进行了模拟，数值研究了峰值电压、脉冲重复频率和 NSDBD 方向排列对防冰性能的影响， 分别。

发现

数值结果与实验数据的一致性表明该方法是准确的。结果表明，防冰区有热空气覆盖。峰值电压和脉冲频率的增加提高了防冰性能，NSDBD的方向布置也影响防冰性能。

原创性/价值

结合结冰算法和现象学模型开发了一种数值策略。讨论了NSDBD的三个参数对防冰性能的影响。预测结果表明，该防冰方法是有效的，可能有助于无人机防冰系统的设计。